Tandem rocket launcher and firing system



Mafch 29, 1960 F. Q JONAH Filed May 9, 1955 5 Sheets-Sheet 1 March 29, 1960 F. c. JoNAH TANDEM `ROCKET LAUNCHER AND FIRING SYSTEM Filed May 9, 1955 5 Sheets-Sheet 2 INVENToR. FREDERICK c. JONAH BY/ M/ if/M ORNEYS March 29, 1960 F.vc. JoNAH 'TANDEM ROCKET LAUNCHER AND FIRING SYSTEM 5 Sheets-Sheet 5 Filed May 9, 1955 Fig. 7

INVENTOR. FREDERICK C. JONAH V A 0 R NE YS March 29, 1960 F. c. JONAH 2,930,288

TANDEM ROCKET LAUNCHER AND FIRING SYSTEM Filed May 9. 1955 5 Sheets-Sheet 4 INVENTOR. FREDERICK C. JONAH Fig.

Ton/VE Ys March 29, 1960 F. c. JONAH TANDEM ROCKET LAUNCHER AND FIRING SYSTEM 5 Sheets-Sheet 5 Filed May 9, 1955 INVENTOR. FREDERICK C. JONAH United States Patenti() F TANDEM ROCKET LUNCHER AND FIRING i SYSTEM v Frederick C. Jonah, Dallas, Tex., assgnor to Chance Vought Aircraft, Incorporated, Dallas, Tex., a corporation of Delaware j Appliation May 9, 195s, serial No. 507,017

s claims. (cl. fis-157) This invention relates to rocketlaunching devices and more particularly to a rocket'pack capableof beingattached to an 'aircraft and of firing rockets in tandem.

The designof aircraft rocket launching devices depends to someV extent on the aircraft design, the desired llight characteristics of the aircraft and the number of rockets to be accommodated. Heretofore, launchers the fuselage; Y Fig. 2-is a front View of the rocket pack partially in capable of carrying large numbers of rockets utilized magazines housed Within the aircraft,. which construction was usually incapable' of being adapted to existingV aircraft, occupied a large space within the fuselage, land permitted a limited rate ofire. Inaddition, such launch- 72,930,288 Patented Mar. 29, 1960 V1C@l A further object is to provide a firing circuit for such a rocket pack operable remotely by an operator to launch preselected groups of rockets in tandem and including precautions to ensure safe operation.

Still other objects are to provide a rocket pack which is capable of being adapted to existing aircraft without excessive modification, and which can be quickly attached and detached from the aircraft for replacement and maintenance.

Other objects and many of the attendant advantages of vthis invention will be readily appreciated as the same becomes better understood by reference to the'followingA detailed description when considered in connection with the accompanying drawings wherein:

the rocket pack of this invention on the underside of section to show the lateral disposition of the rocket tubes and other details;

Fig. 3 is a longitudinal section of the rocket pack taken along line III- III of Fig. 2 showing the tandem arrangement of the rocket tubes, and disposition of the various component devices;

ers 'were complicated and heavier in construction which is a critical factor in present day aircraft design.

It has been found that a properly faired rocket pack shell on an outer surface of the aircraft imposesrvery small penalties in aircraft range, speed, and maneuver-@ ability yvhile providing a maximum rocket load.

.According to thepresent invention a multiple rocket launcher is provided that will house and lire rockets in tandem, one after another. VIn one embodiment the Alauncher is constructed with one or more pairs of laterally spaced rocket tubes disposed in tandem, an aft tube in each pair being axially aligned and spaced froma forward tube through which an aft rocket is propelled after ignition of a forward rocket. To permit theignition of the forward rocket and still have afree tube for passage 0f the aft rocket, the forward firing mechanism is retractable from the firing position in the space between the alignedvtubes, and, in the preferred form, thev firing mechanism is `mountedon a pivotable deectorvdoor which functions to protect the aft rocket from the forward rocket blast. In another embodiment therockets in tandem are supported in a single firing tube. In each modification safety measures are provided forensuring against the firing of an afty rocketuntilfthe corresponding forward rocket is tired..` Each rocket tube is furnishedy with a latch mechanism for retaining the rocket Withinl the tube and preventing accidental displacement vuntil a predetermined rocket thrust is developed. The rocket tubes are housed ina faired shell that is mounted to the underside of the airplane, the shell being quickly attached and detached by a manually `operated latching mechanism. An exit opening is formed in the forward end of the shell through which the rockets are ejected, the opening having a door and an associated switch in the firing circuit to disarm the latter'when'the door is closed. Other safety precautions are provided in the firing circuit to assure safe operation of the rocket pack fwhile the aircraft in Vflight or grounded. l

A principal object of the invention is to provide a rocket pack capable of accommodating a greater rocket load and to attain a high rate of lire without imposing aerodynamic penalties on the supporting aircraft.

Another object is to provide a rocket pack in which a maximum load can be carried in a faired shell having rocket tubes arranged in a single or multiple layer formation. l Y 1 Fig. 4 is an enlarged view, partially in section, ofa pair of fore and aft rocket tubes showing details of the deector door and integral forward rocket tiring mechanism, the door in the midst of being opened by the passage of an aft rocket;

Fig. 5. is a rear perspective view of an aft'n'ng tube and the associated firing mechanism;

Fig. 6 is anenlargedview of a sensing switch, partially in section, mounted on each of the=forward rocket tubes; Fig. 7 is an enlarged longitudinal section of a rocket retaining latch mechanism mounted on each rocket tube Y and illustrated inlatched and released positions;

able by a latching mechanism later to be described. Eachl 1 Fig. 8 is a partial rear perspective view of the afty tfair'ed section in an open position;

` a rocket pack 12 particularly suited for attachment to an under section of the fuselage of a F7U-3 airplane, and having a remotely controlled system for electrically firing 2.75 inch folding-lin air-to-air rockets, although it is to be understood that the invention is vnot necessarily limited to the particular aircraft or to tthe size or type of rocket.v

As illustrated in Figs. 2 and 3, rocket pack12 comprises a plurality of pairs of forward and aft rocket tubes,

each pair beign laterally disposed and comprising tubes 14 and 16 longitudinally aligned in tandem in spaced relation, each tube adapted to carry a rocket. The particular rocket pack shown in Figs. 2 and 3 is constructed to carry thirty-two acceleration armed rockets in two banks, sixteen forward and sixteen aft, although it is obvious that the total number and disposition of the rocket tubes may vary depending on the aerodynamic requirements of any given aircraft. The rockets may be launched in a salvo or portions thereof in a manner later to be described. The rocket tubes are generally mounted at each end by frames 18 within shell 20 faired to the contour of the lowerfuselage, the shell being readily detach- Fig. 1 is a top perspective View of an airplane carrying-` rocket tube` 14 and 16 is open ended and functions as a ring chamber for the respective rocket, and in addition forward tube 14 being in the path of the aft rocket serves as a guide therefor to improve llightcharacteristics of the latter.

AsN the rocket tubes in each bank are identical, the

following description of a typical pair of forward andL aft rocket tubes 14 and lo will apply to all laterally `disposed pairs. It is apparent that three or more banks of rocket tubes could be arranged' in tandem if an additional rocket load is desired and the rocket size and the space available will permit. In order to fire rockets in tandem, it is necessary to clear the forward tube and intermediate space between fore and aft tubes of any ring mechanism and other structure that will interfere with passage of the aft rocket body and fins. This is accomplished in the instant invention by arranging the tiring mechanism to be movable in and out of this space, and as shown in Figs. 3 and i a forward rocket tube firing mechanism 22 is mounted on the forward face of a deflector door 24 pivoted at 26 to frame l. Firing mechanism 22 comprises a conical shaped firing pin 28 slidably mounted in an insulator housing 3i), the pin having a reduced shank 32 around which is positioned a compression .spring 34 normally urging the pin outwardly to engage the forward rocke-t primer, not shown, the outward movement of the pin being limited by a washer 3d upon engagement with the insulator housing. The inward movement ofV pin 23 is limited by the solid height of the springv to prevent the conical surface of the pin from entering the housing and forming a pocket that would vaccumulate residue formed during tiring and jam the pin. A conductor 38' connects the tiring pin to the tiring circuit, hereinafter described, and extends through a longitudinal opening inthe de,- ilector door for protection against the heat of the-blast.

`The adjacent edges of the forwardY and aft rocket tubes A Yare cut on a bias to conform to the pivotall action ofthe deector door which is urged snugly against aft 4tube V15 by a closing spring 4l) to protect the rear rocket from the forward rocket blast. ln a closed position, dellector y24 aligns firing pin 28 with the forward rocket primer ,andv

upon ignition of the forward rocket vdefiects the .blast downwardly and out through an exhaust opening 42 inthe shell, which may be provided with a door 44 spring urged to a closed position and opened by the force of the blast. As is shown in Fig. 4, vdeilector door24 is in the midst of being forced open by the nose of an ignited` rear rocket in and willberetained 4inan open horizontalposiftion to vprevent interference with the passage of the rocket bodyand n assembly by a latch 4S designedto engage a door latch tongue 49. `A latch release `t) accessible through exhaust opening 42 enables thedeector door to be returned to the firing position prior .to reloading of the pack.

i -A typical firing mechanism for the .aft rocketztubes is shown in Fig. 5 and comprises a U-shaped ring pin 52, one leg being rotatably mounted and longitudinally reciprocable in a bracket 54 `mounted on the rocket tube so that the pin can be 'offset from the tube axis for reloading rockets from the aft end. A compression spring 56 -nortions of the tube which is most accessible from outside the pack. One end of arm 62 is provided with a trigger 68 adapted to project througha rocket tube opening 70 as urged by spring 72, the other end of arm 62 being provided with a contact 74 adapted to engage a fixed contact 76 in the absence of a rocket in the forward tube to complete the circuit to the aft firing mechanism and permit firing of the aft rocket, later described with reference to Fig. l0. Normally, ldepression of trigger 68 by a rocket in the forward tube opens the sensingl switch to disarm and ground the aft firing circuit. A door 77 on the bottom of shell 20 provides access to the sensing switch.

.A rocket retaining latch mechanism 78 is mounted on all of the forward and aft rocket tubes, as shown in Figs. 3 and 7, and restrains each rocket in its tube in firing position, preventing accidental displacement as might occur in carrier based aircraft during catapult launching, arrested landings, and emergency landings such as barrier c rashes. Each latch mechanism 7S comprises a latch arm Si) intermediately pivoted at 82 to a pair of brackets 84 which are welded or otherwise attached to each side preferably to the under portion of the rocket tube as is sensing switch `6i). It should be noted that one of the brackets 84 has been removed to show the latch details. One end of arm Si) is providedV with a latch linger E6 capable of protruding through a rocket tube opening 88 and into the tube bore to engage a corresponding rocket recess, not shown, to retain the rocket in position. The other end of arm Si) is connected to a coil spring 9% for resisting any rocket-releasing movement of the latch finger until a predetermined rocket thrust is developed and exerted on latch linger S6. it has been found for 2.75 inch, folding-fin v air-,to-ar rockets that a suitable latch-releasing force is 215 (m35) pounds. To prevent the released latch from interfering with the fin assembly of the respective rocket during egress, or an aft rocket in the case of a forward tube latch mechanism, there is provided a locking arm 92, U-shaped in cross section, and pivoted at 94 to brackets 84 and having an elongated slot 96 at one end to slidably engage a pin 97 secured to the linger end of arm 8l). A hook 9S is pivoted at 99 to bracket 84 and extendsthrough an opening ltitl in the base of arm 92, hook 9S being urged to hook under arm 92 by a spring llljto lock the latch mechanism in a released position, shown in broken lines, when latch arm Si) is tripped by the rocket thrust. The other end of retaining spring'i) is anchored to locking arm `92 and ,urges the latch to the rocket-engaging positiom solid-line position, when hook mally urges the firing pin into contact with the aft rocket v primer 5S. Cooperating means are provided on1the. pin and bracket to limit the movement of the ring pin to-the firing and loading positions. -ln a tandem rocket arrangement having both -forward 98 is manually disengaged. A door 102 is provided in the bottom of shell 2t) for access to the latch mechanism.

A forward exit door 1&4, Figs. 2 and 3, forms a portion of the rocket pack forward fairing and serves as a rocket tube protective cover when the rocket system is not in operation. Door 164 is hinged at fue being actuated to an open position, indicated by broken lines, by a hydraulic cylinder 108, one at each side of the pack, through afshaft 109 and suitable crank-arml linkage H0, Flow to cylinder 108 through pipes 111 to open and close exit door 104 is controlled by an exit door selector valve i12 and associated switch 113 automatically positioned to an open position whentheV pilot lires the rockets, as will be described with reference to Fig. l0. An articulated linkage 1M is connected atone end to the door and at the other end to an exit doorsafety switch 116 connected in the firing-circuit to prevent vfiring of rockets until the exit door is-in thefully open position, that is, the trailing edge of the door rotated counterclockwise above the top surface of the rockettubes. Exit door lldfurtherrprovides access forloading orl unloading the forward rockets, for which purpose theexit door may be controlled from the ground by a manually controlled switch 113 (Fig. 9).

rAs shown in Fig. 8, aft rocket tubes 16 are loadedand unloaded throughV anaft fairingsectionlZil hinged at -1 ,22 andlo'cked in,.olosedmpositionby jan z tctuation'knobhll and associated latch linkage 125. Suitable exhaust operiings maybe provided in section 120 Ato vent the pressure and gasesfrom aft rocket iiririgsv and may be provided withV to permit quick mounting and detachment, which comprises a plurality of manual, independently operated latching mechanisms 128 located at Vspaced locations around the shell as shown in Fig. 3." The edge of shell 20 is provided with a resilient sealing tube 129. adapted to engage the fuselage to seal the connection and absorb any vibration occurring therebetween. The left-handlmechanism shown in Figs. 2 and 9 is illustrative, of the variouslatch mechanisms 128 and, in addition, functions as a master control, constituting an 4interlock -in the tiring circuit to prevent accidental tiring while .theg airplane is grounded.V Each latch mechanism comprises a downwardly extending fitting 130 anchorediin the airplane fuselageV and having a transverse opening 132` in the free end adapted Vto receive a latch pin 134 for locking' the tting "to Yajshell support 136. Latch pin 134 is actuated by locking handle 138, a crank arm 140, and a rod 142, handle 138 being pivoted at `143 adjacent the shell and accessible from the outside of the rocket pack. In the locked position, shown in broken lines, handle 138 'lies at against the shell lbeing retained by a spring 144and pin 134 extends through iitting 130 in contactwith a locking handle limit switch 146 to arm the rocket firing circuit. In the unlocked position shown in solid lines,handle 138 projects normal to the shell retracting pin 134 from tting 130 and switch 146 to disarm the ring circuitiwhich condition is indi-V4 cated by the energizationof a `circuit position light 148. The above described electrical interlock system is prov vided on one of thelatching mechanisms 128, the particular one being a matter of convenience to `permit the disarming of `theiiring circuit by ground personnel for rocket loading, unloading or repairs. Anexit door selector valve limit switch,15v is actuated by`rod '142 when lockinghandle 138 is unlocked to transfer control of exit door operation to manual control switch 118 for t ASelf-sealing, quick-disconnect couplings, not shown, are! provided for the hydraulic and electrical lines, to facilitate installation and removal of the rocket pack and servicing of,` the system. These couplings. `connect the hydraulic lines from exit door selector valve 112 wl1ich.1can be,v

located in the fuselage to the actuating cylinders 108 in the `forward end ofthe rocket pack, and Vconnectl the elec. trical components in the cockpit to the firing circuit com-.

ponents in the rocket pack.- Access to the couplings are through a suitable panel in the shell.

.The rocket tiring .circuit is described with reference to Fig. `10 wherein the 'components are schematically represented in an energized condition ready for ring.: Most control Ycomponents may be located in an elec-Y iiws in two pathsfthfough 4lines' 16s andi. Foliowing'Y the circuit in line 164, power is admitted through a vcircuit breaker 166, for protecting the rocket circuit from overloads, -to an upper pair ofcontacts in locking handle switch 146 (Fig. 9), shown in a locked position by locking handle 138. From switch 146 primary power is connected in line 168 to a rotary rocket quantity v'selector switch 170 operable by the pilot toV select the quantity of rockets to be fired, namely Quarter, Half, and Salvo through tiring circuits in yan intervalometer 171 and impulse timer 172.V VThe lsettings of selector switch 170 and the ensuing rocket ring order through the intervalometer will be hereinafter described. Primary power is also connected by line 173 to the intervalometer and a latching relay 174, the latter shown in an open position, and in line 175 to an exit door time- Vdelay relay,176whichin,a non-tiring position closes exit door 104 (Figs. 2, andV 3) in the forward end of shell 20 by energizing exit door selector Yswitch 113.

through line 178 andthe upper pair of contacts rof exit doorV selector valve limit switch l150,` the latter also being actuated by locking handle 138.

' Rockets are pilot-fired by depression of a bomb-rocket release button 180, conveniently located on-.the pilots control stick handgrip, which connectsl power in line 163 toenergize latching relay 174 when a rotary bomb-rocket selector switch 182 is in a Rocket position. Placing selector switch 182 in an Oi position, opens line 163.

cally opens when ring button 180 is depressed and will remain open for a predetermined elapsed time controlled by relay 176. In the illustrated embodiment, it

has been ,found that'a delay of approximately 0.50

second in relay 176Y after being deenergized in connect.

ing powerlto close the exit'door 104 will ensure that door closing will not interfere with exit of the aft rockets after tiring. As previously described,Y exit door valve 112v is installed in the main pressure line of the utility hydraulic system and controls the position of exit door 104 by regulating fluid to the exit door actuating cylinders 108. Valve 112 is a four-way valve'loperated by switch 113 comprising two solenoids, one for door open and one for door close, with manual override buttons for testing.

. Y Power in line 181 isv also connected by line 183 to exit door safety switch 116 (Fig. 3) connected to impulse timer :172 and prevents tiring of the rockets until the exit door is in the fully open position. v

Referring back to rocket quantity selector switch 170 and intervalometer 17'1, the quantity of the total 32 551 rockets to be launched is determined by the setting of the switch inone of the three positions Quarter (eight tronicszcompartmentY in4 the cockpit, while other'coniv ponents may be located in the. rocket pack. The rocket vtiring circuits arelcontrolled through a master armament circuit located :in the cockpit and includes a master armament switch breaker (Master Armt.) 152, an

armament safety resistor 153, amaster armament relayk 154, a gun safety circuit breaker 156 (Gun Safety) a,

gun firing override relay 158, a landing gear handle ref lay 160 and Yan ,armament.sat`ety disablingswitch (Arm 'Safety"Disable) 162.` When `Master Armt. switch 152 l is turnedto an On.position, primary bus power source islconnectedV to the `rocket ring'circuit through relay 15,4, providing this `relay is not shorted lto ground by relay 160, which occurs when the landing gear handle, not shown, is infdown position'.` Gunv Safety switch 156,

i relay 158 and Arm Safety switch 162l are provided for testoperation of the'rocket pack'system on the ground. Primary bus power `connected "to the ring circuit rockets-two groups of four); Half (sixteen rocketsfour groups of four; or Salvo (thirty-two rocketseight groups of four). Rockets are red as controlled by intervalometerf171 in theorder shown below, the rocket tubes being numbered'from left to right looking forward and are red in the order shown to eliminate aerodynamic and iin interference.

Rocket firing order assess/s Intervalometer 171 is commercially available from Revere Corporation of America, Wallingford, Connecti cut, and electrically selects the group ofv rocketsdtobe tired by connecting power to the tiring circuits, and infcl'udes a series of relays. 186, vone of which is illustrated,

and a group selector 188, showing the eight circuit por sitions. The'intervalometer is armed when Master Armt.

switch 152 is turned to an 0n position, and actuated` when release button 180` is depressed. The interval; ometer is controlled by electrical impulses delivered from impulse timer 172, which consists of an electrical turning fork 190, also commercially available from the Revere Corporation of America, which steps group circuit selector 188 from one ring order circuit position` to the next. The number of impulses delivered by timer 172 is determined by the position of rocket quantity selector switch 170. When group circuit selector is stepped to the last selected` circuit, it transmits a signal to`shut off the firing power to firing circuit selector 188, and on the next impulse it shuts off the stepping impulses from impulse timer 172. This maintains Ytiring circuit selector 188 in position to re `the nt circuit when bomb-rocket release button -180is again depressed.

- The intervalometer will return to and remain in theY No. 1 circuit position from any other circuit position when locking handle v138 is placed in the unlocked p ofly sition for ground operation of the rocket pack system.

In place of intervalometer 171 and timer 172, a simple the ground, locking handle 138 is moved tothe unlocked' position, except when testing continuity of theiringcircuit, which mechanically actuates switches 146` and 150. Operation of limit switch 146 disconnects primary bus power and connects battery'power in line 192 to the rocket tiring system, disarmsthe firing circuits, cycles the intervalometer to the No. 1 firing position, energizes circuit position light 148 (Fig. 9), and connectslpower to ground-operated exit door vcontrol switch 118 in line 194. Unlocking locking handle 138 also operates exit door selector valve limit switch 150 disconnectinglines 178 and 184 from time delay relay 176 and connecting them to lines 196 and 198 to ground operatedv exitv door control switch 118 to enable the exitV door-switch 113 and valve 112 to be manual controlled to open the exit door. t

Operation of the entire rocket pack system `is as follows' assuming Master Armt. switch 152 is On and the landing gear handle is Up When rocket firing button 180 is momentarily depressed, exit door valve 112 ispositioned to allow hydraulic fluid to actuate exit door cylinders 108 and open exit door 104. When exit door 134 is fully open, safety switch 1116 is actuated energizing impulse timer 172 which feeds electrical impulses to the intervalometer 171 to re the selected numher of rockets as determined by the setting of selector switch 171i. All forward rockets are launchedbefore the aft rockets are energized. When a forward rocket is ignited by firing pin 28, a thrust of 2l5 (1 -35) pounds developed'by theu rocket will release it from latch mech'- anism 78. As the forward rocket leaves Vthe tube, it trips sensing switch 60 arming the firing circuit to the aft tiring pin 52. Deflector door 24 normally positioned between the fore and aftVV tubes V14 andflde'llectsmexhaust gases and blast pressure out of shell 2i).y `I-f for any reason the forward rocket misires', sensing switch 60 maintains an open circuit to the aft -ring pin, -prevent. ing the intervalometer from ignitin'gftlie'iooketfidirectiy behind n,the lud ...rocket .When .an -att .rocket is .ignited and develops a thrust of 215 (135) pounds, it trips rocket latch mechanism on tube 16 and cams open deector door 24 which is latched in an open position to avoid interference with the passage of the aftrocket. Exhaust gases and pressure of the Vaft rocket are vented through an exhaust opening in the aft fairing section. A fter firing the selected rockets, intervalometer 171 deenergizes exit door switch 113 which Ycloses exit door 194 and disarms the firing circuit. f

In Figs. 11 and 12 are shown a modified rocket tube arrangement wherein a single open-ended tube 200 is used to house two or more rockets 202 arranged in tandem which rockets may be of a type having a primer band 204 positioned circumferentially around the rocket. Inl such a constructionthe tiring mechanism 206 is 1octed at a longitudinal position on tube 200 adjacent thev rocket primer, the tube having a suitable aperture 207 through which firing mechanism is projected to ignite the primer. The firingl circuit and the arrangement of the pack assembly forl the embodiment of Figs. 11 and l2 maybe similar to that previously described with reference to Figs. 1 through 10. A sensing switch 208 is mounted on tube 200 laterally disposed of the forward rocket to disarm the vfiring circuit to the aft rocket whenever the forward rocket is in the tube, similar in purpose and construction to sensing switch 60 (Figs. 3 and 6).

A plurality of longitudinal rails 210 are formed on the bore of tube 200 to support the rockets in spaced relation thereto, providing longitudinal exhaust passages 212 therebetween to vent the gases and the explosion pressures. Instead of using rails 210 and longitudinal passages 212 to vent the gases, the tube may be smooth and provided with a plurality of drilled transverse apertures, not shown, preferably between the rockets which will be able to vent the gas pressure. Means may also be provided for latching the rockets into the tube, such as retaining latch mechanism 78 (Figs. 3 and 7).

The rocket pack and ring 'system of this invention provides a compact grouping of rockets in stream-lined shell capable of being faired to the fuselage of an aircraft causing a minimum, if any, interference to flight characteristics. Use of a tandem arrangement of rockets permits at least twice the number of rockets to be carried in a single layer arrangement. The rockets are supported in 'tandem within a single tube or two or more longitudinally spaced and aligned tubes each of which constitutes a ring chamber for the respective rocket, while the vforward lportion or tube functions to guide theaft rocket as it passes therethrough. The firing mechanism for the single or multiple tube arrangements is located on vthe tubes, corresponding to the location of the rocket primer. Where the primers are located in the tail end, such as in the 2.75 inch folding tin aircraft rocket, the forward ring mechanism is conveniently located between the rockets and arranged to move out of the way of thev aft fired rocket. A sensing switch associated with the forward tubes ensures that an aft tandem rocket will not iire with a rocket present in the forward tube. .Latch mechanism on each tube prevents accidental displacement of the rockets until a predetermined thrust is exerted by the rockets. Various safety switches in the firing circuit ensures safe operation of all components of the system when tiring in night or when the aircraft is on the ground'. The rocket packl assembly is mechanically 4and electrically quickly detachable from the aircraft bysuitable latching mechanisms and by releasable 4m 1, A rocket launcher device comprising forward and 9 aft longitudinally spaced rocket tubes aligned in tandem each tube capable of supporting a rocket, la firing mechanlsm for each rocket tube, a deflector door mounted on the launcher in the space between said tubes for blocking the aft tube and protecting the rocket in the aft tube from the blast effects of the forward rocket and deflecting the blast effects laterally through the space Abetween said tubes, said deflector door being movable out of the space between saidtubes to permit the free passage of the aft rocket through the forward tube. i

2. The device of claim 1 wherein the firing mechanisrn for the forward tube is mounted on the deflector door. 3. An aircraft rocket-launching device comprising a shell, means for securing the shell to an aircraft, said shell housing a plurality of laterally arranged forward and aft rocket tubes longitudinally spaced in tandem, a

firing circuit for successively igniting-rockets adapted to be supported in said. forward and aft tubes respectively,

a deflector door pivotally mounted in the space-between each pair Vof tandem tubes, a firing pin mounted" on the forward face of the doorV for igniting the rocket in the forward tube, lsaid door` being constructed and arranged to substantially block the aft tube from the blast of the forward rocket when red and .forwardly pivotable` by the passage of theaft rocket to open the aft tube and allow passage of the aft rocket through the forward tube and means for latching said doorin an open position.

4. An aircraft rocket-launching device comprising a shell, lmeans for securing the shell to an aircraft fuselage, said shell housing a plurality of laterally disposed forward and aft rockettubes longitudinally spaced in tandem, a tiring circuit for successively igniting rockets adapted to be supported in said forward and aft tubes respectively, a switch mounted oneach forward tube for disarming the ring circuit to the corresponding aft tube when a rocket is present in the forward tube, releasable latch means on the tubes for holding the respective rockets in the `tubes until released by a predetermined firing thrust, means for locking said forward latches in a released position after the forward rocket is fired, a deector door pivotally mounted in the space between each pair of tandem tubes and normally in a position to block the aft tube from the blast of the forward rocket when fired, said door being pivotable to `an offset position to open the aft tube to enable free passage of the aft rocket through the forward tube. u

5. An aircraft rocket launchingV` device comprising a ward tube, a releasable latch means on each tube vfor holding the respective rockets in the tube until released by a predetermined lring thrust, said-shell having an exit opening aligned with the tubes through which the rockets are discharged, a door for closing said opening, means for opening the door, and a switch operable by the door opening means to disarm the firing circuit whenthe door is closed.

6. A rocket launcher device comprising a rocket tube arrangement providing a ring chamber for a plurality of longitudinally spaced rockets snugly supported in ring position in tandem one behind the other, a plurality of firing mechanisms mounted on said tube arrangement, one for each of said rockets, said ring mechanism for the forward rocket extending into the bore of the tube arrangement for igniting the respective rocket and being retractable from the firing position to a retracted position completely outside the tube bore to permit the free passage of an aft rocket.

7. The rocket launcher of claim 6 wherein each rocket is mounted'in a separate tube longitudinally spaced in tandem, and said firing mechanism for the forward tube is movable in said space between the tubes.

8. An aircraft rocket-launching device comprising a shell, means for securing the shell to an aircraft, said shell housing a plurality of laterally arranged forward and aft rocket tubes longitudinally aligned and spaced in tandem, a firing circuit including a' iring mechanism for each, tube for successively igniting rockets adapted to be supported in said forward and aft tube respectively whereby each aft rocket can be propelled through said aligned'forward tube after ignition of the forward g rocket, an interlock switch mounted on each of the forshell, means for detachably securing the shell to anv airto enable free passage ofthe aft rocket through the for- Wardtube, a ring-pinmechanism for the forwardltube mounted on the dellectordoor, a switch mounted on each p forward tube for disarming the ring circuit to the corresponding aft tube when a rocket is present the forward tubes for opening the firing circuit to the respective aft tubes whenever a rocket is present in the forward tube, said switch being tripped by the movement of the4 forward rocket to close the firing circuit to the aft rocket, a deflector door pivotally mounted between each` References Cited in the file of this patent UNITED STATES PATENTS 2,313,030 Tauschek Mar.` 2, 1943 2,398,871k Turnbull et al Apr. 23, 1946 2,409,210 Jolly Oct. 16, 1946 2,421,893 Lambert et al June 10, 1947 2,445,235 VMyers July 13, 1948 2,451,522 Uhl et al. Oct. 19, 1948 2,478,774 Meinel Aug. 9, 1949 2,496,316 Skinner et al. Feb. 7, 1950 2,517,333 Motley Aug. 1, 1950 2,546,823 Holloway Mar. 27 1951 2,609,730 Bergstrom Sept. 9, 1952 2,690,124 Melick ,Sept. 28, 1954 2,696,143 1954 2,780,143 Graham Feb. 5, 1957 FOREIGN PATENTS 914,341V

France Iune 17, 1946 

